UNCLASSIFIED
PE NUMBER: 0603216F
PE TITLE: Aerospace Propulsion and Power Technology
DATE
Exhibit R-2, RDT&E Budget Item Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and Power Technology
Cost ($ in Millions)
FY 2004
Actual
86.720
3.352
3.207
26.887
11.649
14.433
FY 2005
Estimate
86.050
0.371
5.250
22.420
5.986
26.069
FY 2006
Estimate
77.268
0.196
4.028
18.430
6.627
23.212
FY 2007
Estimate
86.690
2.834
5.588
14.172
4.784
33.780
FY 2008
Estimate
88.391
4.743
6.044
24.777
4.787
22.494
Total Program Element (PE) Cost
Aerospace Fuels
Aerospace Power Technology
Aircraft Propulsion Subsystems Int
Space & Missile Rocket Propulsion
Advanced Aerospace Propulsion
Advanced Turbine Engine Gas
681B
27.192
25.954
24.775
25.532
25.546
Generator
Note: In FY 2005-2007, a portion of the funding in Projects 2480 and 4921 was shifted to Project 5098.
2480
3035
4921
4922
5098
FY 2009
Estimate
92.907
5.156
4.542
26.841
5.191
23.471
FY 2010
Estimate
94.858
5.262
4.636
27.408
5.301
23.964
FY 2011
Estimate
96.622
5.358
4.723
27.918
5.400
24.411
Cost to
Complete
Continuing
Continuing
Continuing
Continuing
Continuing
Continuing
27.706
28.287
28.812
Continuing
Total
TBD
TBD
TBD
TBD
TBD
TBD
TBD
(U) A. Mission Description and Budget Item Justification
This program develops and demonstrates technologies to achieve enabling and revolutionary advances in turbine, advanced cycle, and rocket propulsion, as well as
power generation and storage, and fuels. The program has six projects, each focusing on technologies with a high potential to enhance the performance of existing and
future Air Force weapons systems. The Aerospace Fuels and Atmospheric Propulsion project develops and demonstrates improved hydrocarbon fuels and advanced
propulsion systems for high-speed/hypersonic flight. The Aerospace Power Technologies project develops and demonstrates power and thermal systems for weapons
and aircraft. The Advanced Turbine Engine Gas Generator (ATEGG) project develops and demonstrates core turbine engine technologies for current and future
aircraft propulsion systems. The Aerospace Propulsion Subsystem Integration project integrates the engine cores demonstrated in the ATEGG project with
low-pressure components into demonstrator engines. Turbine engine propulsion projects within this program are part of the Integrated High Performance Turbine
Engine Technology and the Versatile Affordable Advanced Turbine Engine programs. The Advanced Aerospace Propulsion project develops the scramjet propulsion
cycle to a technology readiness level appropriate for in-flight demonstration and for full integration with other engine cycles (including turbine and rocket based).
Finally, the Space and Missile Rocket Technology project develops and demonstrates innovative rocket propulsion technologies, propellants, and manufacturing
techniques. Rocket propulsion projects within this program are part of the Integrated High Payoff Rocket Propulsion Technology program, which includes the area of
Technology for the Sustainment of Strategic Systems. Note: In FY 2005, Congress added $1.0 million for Advanced Satellite Thermal Control Program; $2.4 million
for Versatile Affordable Advanced Turbine Engine; and $3.5 million for Integrated High Performance Turbine Engine Technology Phase III Technology
Demonstrator. This program is in Budget Activity 3, Advanced Technology Development, since it develops and demonstrates technologies for existing system
upgrades and/or new system developments that have military utility and address warfighter needs.
R-1 Shopping List - Item No. 20-1 of 20-22
387
UNCLASSIFIED
Exhibit R-2 (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2, RDT&E Budget Item Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and Power Technology
(U) B. Program Change Summary ($ in Millions)
FY 2004
93.425
86.720
-6.705
(U)
(U)
(U)
(U)
Previous President's Budget
Current PBR/President's Budget
Total Adjustments
Congressional Program Reductions
Congressional Rescissions
Congressional Increases
Reprogrammings
SBIR/STTR Transfer
(U) Significant Program Changes:
Not Applicable.
FY 2005
79.914
86.050
6.136
FY 2006
68.626
77.268
FY 2007
74.950
86.690
-0.764
6.900
-2.347
-4.358
C. Performance Metrics
(U) Under Development.
R-1 Shopping List - Item No. 20-2 of 20-22
388
UNCLASSIFIED
Exhibit R-2 (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 2480 Aerospace Fuels
Power Technology
FY 2004
FY 2005
FY 2006
FY 2007
FY 2008
Actual
Estimate
Estimate
Estimate
Estimate
2480 Aerospace Fuels
3.352
0.371
0.196
2.834
4.743
Quantity of RDT&E Articles
0
0
0
0
0
Note: In FY 2005-2007, a protion of the funding in this project was shifted to Project 5098 in this PE.
Cost ($ in Millions)
PROJECT NUMBER AND TITLE
FY 2009
Estimate
5.156
0
FY 2010
Estimate
5.262
0
FY 2011
Estimate
5.358
0
Cost to
Complete
Continuing
Total
TBD
(U) A. Mission Description and Budget Item Justification
This project develops and demonstrates improved hydrocarbon fuels and advanced, novel aerospace propulsion systems, including systems for high-speed/hypersonic
flight and technology to increase turbine engine operational reliability, durability, mission flexibility, and performance while reducing weight, fuel consumption, and
cost of ownership. The advanced fuel emphasis is on developing and demonstrating new thermally stable, high-heat sink, and controlled chemically reacting fuels for
a conventional turbine engine, turbine-based combined cycle engines, and other advanced propulsion systems. The project also develops and demonstrates fuel system
components that minimize cost, reduce maintenance, and improve performance of future aerospace systems. The advanced propulsion emphasis is on demonstrating
concepts for combined cycle, ramjet, and scramjet engines. This project is integrated into the Versatile Affordable Advanced Turbine Engine program.
(U) B. Accomplishments/Planned Program ($ in Millions)
(U) MAJOR THRUST: Demonstrate thermally stable fuels and fuel system hardware concepts to enhance
cooling capacity (performance), minimize fuel coking, and reduce fuel system maintenance. Note: Due
to FY 2005-2007 funding shifts, the FY 2004-2005 high heat sink fuel technologies demonstration
efforts were slipped for completion in post-FY 2007.
(U) In FY 2004: Studied, tested, and demonstrated, at a pilot-light level, advanced high-heat sink fuels and
hardware concepts that can increase fuel delivery system durability and performance at high temperatures
and can reduce maintenance due to fuel degradation in aircraft fuel systems and engine control hardware.
Developed bread-board, on-engine fuel additive injection hardware. Demonstrated long-term JP-8+225
performance in bench and full-scale fuel systems. Initiated demonstrations of the performance of fuel
developed from alternative (non-petroleum) sources in reduced scale fuel system simulators.
(U) In FY 2005: Continue to study, test, and demonstrate, at a pilot-light level, advanced high heat sink fuels
and hardware concepts that can increase fuel delivery system durability and performance at high
temperatures and reduce maintenance due to fuel degradation in an aircraft fuel system and engine
control hardware.
(U) In FY 2006: Continue to study, test, and demonstrate at a pilot-light level, advanced high heat sink fuels
including those produced from alternative energy resources and hardware concepts that can increase
engine performance at high temperatures, improve fuel system durability, and reduce maintenance due to
fuel degradation in aircraft and engine hardware.
(U) In FY 2007: Continue to study, test, and demonstrate, advanced high heat sink fuels including those
produced from alternative energy resources and hardware concepts that can increase engine performance
Project 2480
R-1 Shopping List - Item No. 20-3 of 20-22
389
UNCLASSIFIED
FY 2004
0.868
FY 2005
0.060
FY 2006
0.025
FY 2007
0.989
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
PROJECT NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 2480 Aerospace Fuels
Power Technology
at high temperatures, improve fuel system durability, and reduce maintenance due to fuel degradation in
aircraft and engine hardware. Initiate demonstrations of fuel performance at fuel temperatures in the
supercritical regime.
(U)
(U) MAJOR THRUST: Determine fuel cooling requirements and specifications for advanced aircraft sensors
and directed energy weapons that will meet the needs of evolving manned systems and unmanned aerial
vehicle (UAVs). Note: Due to FY 2005-2007 funding shifts, the FY 2004-2005 UAV fuel additive
efforts were revised for a restart in post-FY 2007.
(U) In FY 2004: Demonstrated, at a pilot-light level, low temperature additives for use in jet fuel to allow
advanced manned and unmanned systems to sustain high altitude loiter for extended periods. Refined the
design and building an UAV fuel system/tank simulator to study low temperature fuel behavior.
Demonstrated additive performance in aircraft like fuel system simulator.
(U) In FY 2005: Continue pilot-light level demonstrations of low temperature additives for use in jet fuel to
allow advanced manned and unmanned systems to sustain high altitude loiter for extended periods with
focus on combustion performance of additized fuels.
(U) In FY 2006: Continue, at a pilot-light level, to study, test, and demonstrate advanced fuels for UAV
applications including advanced low temperature fuels and fuels to enable extended range and duration.
(U) In FY 2007: Demonstrate advanced low temperature and enhanced performance fuels for UAV
applications focusing on technologies that expand the flight envelope, range, or duration of UAVs to
include advanced thermal management concepts.
(U)
(U) MAJOR THRUST: Develop and demonstrate efficacy of low-cost, environmentally friendly fuel
additives to reduce soot particulate emissions from gas turbine engines using advanced research
combustors and small turbine engines. Note: Due to FY 2005-2007 funding shifts, the FY 2005
combined cycle engine fuel additive efforts were revised for a restart in post-FY 2007.
(U) In FY 2004: Advanced pilot-light level demonstrations of additives that reduce soot emissions by at least
50 percent. Developed additives to improve ignition and combustion characteristics in current and
advanced propulsion concepts, including combined cycle engines. Qualified additives through material
compatibility, toxicology, and hot section tests, and demonstrated additive effectiveness in engine
component tests.
(U) In FY 2005: Continue pilot-light level demonstrations of additives that reduce soot emissions by at least
50 percent.
(U) In FY 2006: Continue pilot-light level demonstrations of additives that reduce soot emissions by at least
50 percent.
Project 2480
R-1 Shopping List - Item No. 20-4 of 20-22
390
UNCLASSIFIED
0.448
0.147
0.025
0.500
0.867
0.060
0.025
0.500
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 2480 Aerospace Fuels
Power Technology
(U) In FY 2007: Demonstrate advanced additives to reduce soot and nitrogen oxides emissions in advanced
propulsion concepts including combined cycle engines.
(U)
(U) MAJOR THRUST: Develop and demonstrate enhancements to fuel system technology. Note: Due to
FY 2005-2007 funding shifts, the FY 2005 combined cycle engine candidate/hardware efforts were
revised for a restart in post-FY 2007.
(U) In FY 2004: Designed and developed concept hardware and fuel system simulators to evaluate key high
temperature fuel system components of reusable aerospace vehicles, focusing on aerospace vehicles with
advanced and combined cycle engines that require high levels of fuel cooling. Improved characterization
of hydrocarbon fuel candidates and enhanced hardware concepts for combined cycle engines.
(U) In FY 2005: Continue pilot-light level design and development of hardware and fuel system simulators
to evaluate key high temperature fuel system components of reusable aerospace vehicles focusing on
aerospace vehicles with advanced and combined cycle engines that require high levels of fuel cooling.
(U) In FY 2006: Continue pilot-light level design and development of hardware and fuel system simulators
to evaluate key high temperature fuel system components of reusable aerospace vehicles focusing on
aerospace vehicles with advanced and combined cycle engines that require high levels of fuel cooling.
(U) In FY 2007: Continue design, development, and demonstration of hardware and fuel system simulators
to evaluate key high temperature fuel system components of reusable aerospace vehicles focusing on
aerospace vehicles with advanced and combined cycle engines that require high levels of cooling.
(U)
(U) MAJOR THRUST: Identify, develop, and demonstrate low-cost approaches to reducing the fuel logistics
footprint for the Expeditionary Air Force. Note: Due to FY 2005-2007 funding shifts, the FY 2005
novel nozzle efforts were revised for a restart in post-FY 2007.
(U) In FY 2004: Furthered pilot-light development of novel methods for fuel analysis and additization in
order to extend the usable temperature range of commercially available aviation fuel through application
of novel technologies, including biologically related approaches. Demonstrated applicability of rapid
fuel screening and identification using chromatography-based statistical analysis methods and
commercially available fuel analyzers.
(U) In FY 2005: Continue pilot-light development of novel methods including bio- and nano-technology for
fuel analysis.
(U) In FY 2006: Continue pilot-light development of novel methods including bio- and nano-technology for
fuel analysis.
(U) In FY 2007: Demonstrate advanced nano-technology fuel additives, nano-technology fuel sensors, and
novel detection and mitigation technologies for biological growth.
Project 2480
R-1 Shopping List - Item No. 20-5 of 20-22
391
UNCLASSIFIED
PROJECT NUMBER AND TITLE
0.737
0.057
0.025
0.345
0.432
0.047
0.096
0.500
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 2480 Aerospace Fuels
Power Technology
(U)
(U) Total Cost
(U) C. Other Program Funding Summary ($ in Millions)
FY 2004
FY 2005
Actual
Estimate
(U) Related Activities:
PE 0602203F, Aerospace
(U)
Propulsion.
(U) PE 0602102F, Materials.
PE 0602204F, Aerospace
(U)
Sensors.
PE 0603112F, Advanced
(U) Materials for Weapons
Systems.
This project has been
coordinated through the
(U) Reliance process to
harmonize efforts and
eliminate duplication.
(U)
PROJECT NUMBER AND TITLE
3.352
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
FY 2009
Estimate
FY 2010
Estimate
0.371
FY 2011
Estimate
0.196
2.834
Cost to
Total Cost
Complete
D. Acquisition Strategy
Not Applicable.
Project 2480
R-1 Shopping List - Item No. 20-6 of 20-22
392
UNCLASSIFIED
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 3035 Aerospace Power Technology
Power Technology
Cost ($ in Millions)
3035
Aerospace Power Technology
Quantity of RDT&E Articles
FY 2004
Actual
3.207
0
FY 2005
Estimate
5.250
0
FY 2006
Estimate
4.028
0
FY 2007
Estimate
5.588
0
FY 2008
Estimate
6.044
0
PROJECT NUMBER AND TITLE
FY 2009
Estimate
4.542
0
FY 2010
Estimate
4.636
0
FY 2011
Estimate
4.723
0
Cost to
Complete
Continuing
Total
TBD
(U) A. Mission Description and Budget Item Justification
This project develops and demonstrates electrical power generation, energy storage, thermal management, and distribution systems for aerospace applications. This
technology enhances reliability and survivability, and reduces vulnerability, weight, and life cycle costs for manned and unmanned aerospace vehicles. The electrical
power system components developed are projected to provide a two- to five-fold improvement in aircraft reliability and maintainability, and a 20 percent reduction in
power system weight. This project also develops and demonstrates high power generation, energy storage, and thermal management technologies to enable high power
density sources for directed energy weapons.
(U) B. Accomplishments/Planned Program ($ in Millions)
(U) MAJOR THRUST: Develop power generation and conditioning, high rate batteries, and energy storage
component and subsystem technologies for integration of high power subsystems with directed energy
weapons (DEW). These technologies will enable the delivery of high power for operation of DEW.
Note: FY 2005 low duty cycle generator system efforts have been delayed until FY 2006 and FY 2006
synergistic efforts have been delayed to FY 2007 to allow for multi-megawatt superconducting Applied
Research activities to more fully develop. In FY 2006, the megawatt superconducting power system
demonstration activity will be moved to a separate effort in this Project.
(U) In FY 2004: Completed fabrication and tests of a high power, low duty cycle generator critical
components for pulsed DEWs.
(U) In FY 2005: Initiate analysis of power system integration into an airframe as part of a non-lethal weapon
system. Initiate preliminary design of and develop analytical model for a megawatt class power system
demonstrator.
(U) In FY 2006: Develop technology roadmaps and complete analysis of power system integration into an
airframe as part of a non-lethal weapon system. Initiate design for a megawatt non-superconducting low
duty cycle generator system tailored to directed energy weapons.
(U) In FY 2007: Complete design and perform modeling and simulation of a megawatt non-superconducting
low duty cycle generator system tailored to directed energy weapons.
(U)
(U) MAJOR THRUST: Develop power generation/conditioning/distribution component, energy storage, and
thermal management components and subsystem technologies for manned and unmanned aircraft
systems. These technologies will improve aircraft self-sufficiency, reliability, maintainability, and
supportability, while reducing life cycle costs and enabling new capabilities. Note: In FY 2006, this
Project 3035
R-1 Shopping List - Item No. 20-7 of 20-22
393
UNCLASSIFIED
FY 2004
0.912
FY 2005
1.701
FY 2006
0.990
FY 2007
0.907
1.566
1.795
1.267
0.000
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 3035 Aerospace Power Technology
Power Technology
activity will be completed.
(U) In FY 2004: Initiated design of the demonstration electrical generator for integration into mid-thrust
class engines. Fabricated and tested large amp-hour (200) cells and batteries.
(U) In FY 2005: Complete detailed design of demonstration electrical generator for integration into
mid-thrust class engines.
(U) In FY 2006: Complete engine integration and test of the internal starter generator in mid-thrust class
engines.
(U) In FY 2007: Not Applicable.
(U)
(U) MAJOR THRUST: Develop power generation/conditioning/distribution, energy storage, and thermal
management components and subsystem technologies that are synergistic with aerospace and weapons
platforms.
(U) In FY 2004: Fabricated low volume/low weight high temperature motor drive.
(U) In FY 2005: Test low volume/low weight high temperature motor drive.
(U) In FY 2006: Not Applicable. Note: The FY 2006 synergistic efforts will be delayed to FY 2007 to
allow for multi-megawatt superconducting Applied Research activities to more fully develop.
(U) In FY 2007: Investigate alternative energy storage/generation systems for low power applications.
(U)
(U) MAJOR THRUST: Develop analytical tools and subsystems for multi-megawatt superconducting
electrical power systems including power generation, conditioning, and dynamic interaction. Note: Prior
to FY 2006, the megawatt superconducting power system demonstration activity was included in the
directed energy weapons effort in this Project.
(U) In FY 2004: Not Applicable.
(U) In FY 2005: Not Applicable.
(U) In FY 2006: Complete preliminary design for a megawatt class power system demonstrator.
(U) In FY 2007: Initiate detailed design of megawatt class power system demonstrator and begin fabrication
of key components.
(U)
(U) CONGRESSIONAL ADD: Advanced Satellite Thermal Control Program.
(U) In FY 2004: Not Applicable.
(U) In FY 2005: Expand Electrochromics Coatings (EC) productions beyond the pilot scale level, develop
processes incorporating EC into thin flexible films that can be bonded to satellite structures and test EC
devices in real application environments.
(U) In FY 2006: Not Applicable.
Project 3035
R-1 Shopping List - Item No. 20-8 of 20-22
394
UNCLASSIFIED
PROJECT NUMBER AND TITLE
0.729
0.763
0.000
1.450
0.000
0.000
1.771
3.231
0.000
0.991
0.000
0.000
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 3035 Aerospace Power Technology
Power Technology
(U) In FY 2007: Not Applicable.
(U) Total Cost
(U) C. Other Program Funding Summary ($ in Millions)
FY 2004
FY 2005
Actual
Estimate
(U) Related Activities:
PE 0602201F, Aerospace
(U)
Flight Dynamics.
PE 0602203F, Aerospace
(U)
Propulsion.
PE 0602605F, Directed
(U)
Energy Technology.
PE 0603605F, Advanced
(U)
Weapons Technology.
This project has been
coordinated through the
(U) Reliance process to
harmonize efforts and
eliminate duplication.
(U)
PROJECT NUMBER AND TITLE
3.207
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
FY 2009
Estimate
FY 2010
Estimate
5.250
FY 2011
Estimate
4.028
5.588
Cost to
Total Cost
Complete
D. Acquisition Strategy
Not Applicable.
Project 3035
R-1 Shopping List - Item No. 20-9 of 20-22
395
UNCLASSIFIED
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4921 Aircraft Propulsion Subsystems
Power Technology
Int
FY 2004
FY 2005
FY 2006
FY 2007
FY 2008
Actual
Estimate
Estimate
Estimate
Estimate
4921 Aircraft Propulsion Subsystems Int
26.887
22.420
18.430
14.172
24.777
Quantity of RDT&E Articles
0
0
0
0
0
Note: In FY 2005-2007, a portion of the funding in this project was shifted to Project 5098 in this PE.
Cost ($ in Millions)
PROJECT NUMBER AND TITLE
FY 2009
Estimate
26.841
0
FY 2010
Estimate
27.408
0
FY 2011
Estimate
27.918
0
Cost to
Complete
Continuing
Total
TBD
(U) A. Mission Description and Budget Item Justification
This project develops and demonstrates technology to increase turbine engine operational reliability, durability, mission flexibility, and performance while reducing
weight, fuel consumption, and cost of ownership. This project includes the Aerospace Propulsion Subsystems Integration (APSI) program which includes
demonstrator engines such as the Joint Technology Demonstrator Engine for manned systems and the Joint Expendable Turbine Engine Concept for unmanned air
vehicle and cruise missile applications. The demonstrator engines integrate the core (high-pressure spool) technology developed under the Advanced Turbine Engine
Gas Generator project with the engine (low-pressure spool) technology such as fans, turbines, engine controls, mechanical systems, exhaust nozzles, and augmentors.
Additionally, these efforts include activities under the national High Cycle Fatigue program. This project also focuses on system integration of inlets, nozzles,
engine/airframe compatibility, and power and thermal management subsystems technologies. APSI provides aircraft with potential for longer range and higher cruise
speeds with lower specific fuel consumption, surge power for successful engagements, high sortie rates with reduced maintenance, reduced life cycle cost, and
improved survivability, resulting in increased mission effectiveness. Technologies developed are applicable to sustained high-speed vehicles and responsive space
launch. APSI supports the goals of the national Integrated High Performance Turbine Engine Technology (IHPTET) program, which is focused on doubling turbine
engine propulsion capabilities while reducing cost of ownership. Anticipated technology advances include turbine engine improvements providing an approximate 30
percent reduction in tactical fighter aircraft takeoff gross weight and 100 percent increase in aircraft range/loiter. APSI is also fully integrated into the Versatile
Affordable Advanced Turbine Engine program (VAATE). The IHPTET and VAATE programs provide continuous technology transition for military turbine engine
upgrades and derivatives, and have the added dual-use benefit of enhancing the United States turbine engine industry's international competitiveness.
(U) B. Accomplishments/Planned Program ($ in Millions)
(U) MAJOR THRUST: Design, fabricate, and demonstrate durability and integration technologies for
turbofan/turbojet engines. These technologies will improve durability, supportability, and affordability
of current and future Air Force aircraft. Note: In FY 2004, the Air Force refocused turbine efforts to
complete the IHPTET by 2005 causing sustained supersonic engines advancement efforts to be reduced
in FY 2004 and future efforts to be delayed until FY 2006. Additionally, as a consolidation process,
these efforts were shifted to the improved performance and fuel consumption effort in this Project.
(U) In FY 2004: Completed structural durability tests of an engine and performance tests of the Joint
Technology Demonstrator Engine containing fixed inlet guide vanes and a Moderate Aspect Ratio rotor,
fan rim damper, High Cycle Fatigue mistuning and damping technologies, vaneless counter-rotating
high/low pressure turbine, probabilistic rotor system design, sprayform cast turbine case, and a high
fuel/air ratio Impingement Film Floatwall Combustor. Initiated advanced engine designs for a sustained
supersonic engine with advanced aero, a low pressure turbine with advanced thermal barrier coatings and
Project 4921
R-1 Shopping List - Item No. 20-10 of 20-22
396
UNCLASSIFIED
FY 2004
5.744
FY 2005
1.777
FY 2006
1.400
FY 2007
1.300
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4921 Aircraft Propulsion Subsystems
Power Technology
Int
microcircuit cooling scheme, thermoplastic externals and health monitoring.
(U) In FY 2005: Validate the High Cycle Fatigue Test Protocol by completing structural durability tests of
advanced engine components and instrumentation.
(U) In FY 2006: Design and develop agile combat support engine technologies to increase durability of
components to include advanced aerodynamics for fans, turbines, mechanical systems, interactions
between the inlet and fan, and controls/accessories.
(U) In FY 2007: Fabricate and test agile combat support engine technologies to increase durability of
components to include advanced aerodynamics for fans, turbines, mechanical systems, interactions
between the inlet and fan, and controls/accessories.
(U)
(U) MAJOR THRUST: Design, fabricate, and test advanced component technologies for improved
performance and fuel consumption of turbofan/turbojet engines for fighters, bombers, sustained
supersonic and hypersonic cruise vehicles, and transports. Each of these component technology
innovations can be applied to a significant part of the Air Force's engine inventory and offer potentially
significant performance enhancements to future aircraft engineers. Note: In FY 2004 and FY 2005, for
the Low Pressure Turbine efforts, Ceramic Matrix Composites (CMCs) replaced Organic Matrix
Composites (OMCs) due to maturity of the technology.
(U) In FY 2004: Completed fabrication, instrumentation, and assembly, and initiated test of a High Cycle
Fatigue (HCF) robust front frame, an affordable OMC fan frame, a multi-stage forward swept fan, a
damped low-pressure turbine (LPT) blade, a Titanium Matrix Composite (TMC) shaft, and model-based
flexible control with diagnostics in an advanced demonstrator engine. Enhanced advanced engine
designs for an uncooled CMC LPT blade and completed design of a carbon counter-rotating intershaft
seal and active augmentor screech control.
(U) In FY 2005: Complete test of a HCF robust front frame, an affordable OMC fan frame and duct, a
multi-stage forward swept fan, a damped LPT blade, a TMC shaft, and model-based flexible control with
diagnostics. Complete advanced engine designs with an uncooled CMC LPT blade and begin fabrication
of multi-property rotor, fluidic control and modulated turbine cooling.
(U) In FY 2006: Complete fabrication and testing multi-property rotor, fluidic control, and modulated
turbine cooling. Initiate advanced designs for lightweight engine (utilizes a hollow fan, radial
compressor, and low profile combustor) capable of operating as primary propulsion or in a lift mode.
Initiate advanced engine designs for a sustained supersonic engine using variable cycle features, an
advanced fan, improved turbine using cooled metal and cooled CMCs, and lightweight CMC cases and
ducts.
(U) In FY 2007: Enhance advanced designs for lightweight high bypass engine (utilizes a hollow fan, radial
Project 4921
R-1 Shopping List - Item No. 20-11 of 20-22
397
UNCLASSIFIED
PROJECT NUMBER AND TITLE
14.806
11.925
11.374
9.022
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
PROJECT NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4921 Aircraft Propulsion Subsystems
Power Technology
Int
compressor, and low profile combustor) capable of operating as primary propulsion or in a lift mode.
Enhance advanced engine designs for a sustained supersonic engine using variable cycle features, an
advanced fan, improved turbine using cooled metal and cooled CMCs, and lightweight CMC cases and
ducts.
(U)
(U) MAJOR THRUST: Design, fabricate, and test advanced component technologies for limited life
engines. These technologies improve the performance, durability, and affordability of engines for missile
and unmanned air vehicles (UAVs), and subsonic to hypersonic weapon applications.
(U) In FY 2004: Completed engine structural durability testing a high stage loading splittered fan and
uncooled ceramic low-pressure turbine. Completed testing of an uncooled ceramic high-pressure turbine,
and slinger combustor. Completed testing a low volume combustor. Completed fabrication and
conducted durability test an uncooled Ceramic Matrix Composite turbine blisk/nozzle, and a
Carbon/Carbon exhaust nozzle. Initiated designs of advanced component technologies for intelligent and
durability engine test.
(U) In FY 2005: Enhance designs of advanced component technologies for intelligent and durability engine
testing for UAVs. Initiate designs of advanced component technologies for intelligent and durability
engine testing to include an advanced fan/compressor, a ceramic turbine, turbine with new advanced
cooling approach, and improved oil-less bearings.
(U) In FY 2006: Enhance design and begin fabrication of advanced high temperature cooled turbine blade
and combustor for UAV applications. Enhance designs of advanced components for technologies for
intelligent and durability engine testing to include an advanced fan/compressor, a ceramic turbine,
turbine with new advanced cooling approach, and oil-less bearings.
(U) In FY 2007: Continue fabrication of advanced high temperature cooled turbine blade and combustor for
UAV applications. Begin fabrication of advanced components for technologies for intelligent and
durability engine testing to include an advanced fan/compressor, a ceramic turbine, turbine with new
advanced cooling approach, and oil-less bearings.
(U)
(U) CONGRESSIONAL ADD: IHPTET Phase III Technology Demonstrator. Note: In FY 2004, this was
referred to as "Advanced Turbine Engine Gas Generator and Aircraft Propulsion Subsystem Integration."
(U) In FY 2004: Designed and fabricated advanced component technologies for improved performance and
fuel consumption of turbofan/turbojet engines for fighters, bombers, and transports. Refurbished,
fabricated, instrumented, and assembled hardware from the advanced turbine engine gas generator. This
gas generator will be used in engine testing the following components: two-stage forward swept fan;
uncooled CMC low pressure turbine vane; Titanium Matrix Composite shaft; and model-based flexible
Project 4921
R-1 Shopping List - Item No. 20-12 of 20-22
398
UNCLASSIFIED
3.921
2.870
5.656
3.850
2.416
3.469
0.000
0.000
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4921 Aircraft Propulsion Subsystems
Power Technology
Int
control with diagnostics. Each of these component technology innovations can be applied to the Air
Force's engine inventory and offer potentially significant performance enhancements to future aircraft
engines.
(U) In FY 2005: Complete design, fabrication, instrumentation, assembly, and test of a multi-stage forward
swept fan, an uncooled CMC low pressure turbine blade, and fluidic thrust vectoring in an advanced
demonstrator engine.
(U) In FY 2006: Not Applicable.
(U) In FY 2007: Not Applicable.
(U)
(U) CONGRESSIONAL ADD: VAATE. Note: Only for the XTC 58F/1 for purposes demonstrating the
integration of individual technologies for highly fuel efficient 10,000-15,000 pound thrust demonstrator
engines needed for evolving UAVs.
(U) In FY 2004: Not Applicable.
(U) In FY 2005: Initiate designs of advanced component technologies (includes an advanced fan and
improved high temperature turbine blades) for intelligent and durability engine testing for UAVs.
(U) In FY 2006: Not Applicable.
(U) In FY 2007: Not Applicable.
(U) Total Cost
(U) C. Other Program Funding Summary ($ in Millions)
FY 2004
FY 2005
Actual
Estimate
(U) Related Activities
PE 0602201F, Aerospace
(U)
Flight Dynamics.
PE 0602203F, Aerospace
(U)
Propulsion.
PE 0603003A, Aviation
(U)
Advanced Technology.
This project has been
coordinated through the
(U) Reliance process to
harmonize efforts and
eliminate duplication.
Project 4921
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
R-1 Shopping List - Item No. 20-13 of 20-22
399
UNCLASSIFIED
PROJECT NUMBER AND TITLE
0.000
2.379
0.000
0.000
26.887
22.420
18.430
14.172
FY 2009
Estimate
FY 2010
Estimate
FY 2011
Estimate
Cost to
Total Cost
Complete
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
Exhibit R-2a, RDT&E Project Justification
DATE
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4921 Aircraft Propulsion Subsystems
Power Technology
Int
(U)
PROJECT NUMBER AND TITLE
D. Acquisition Strategy
Not Applicable.
Project 4921
R-1 Shopping List - Item No. 20-14 of 20-22
400
UNCLASSIFIED
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4922 Space & Missile Rocket
Power Technology
Propulsion
Cost ($ in Millions)
4922
Space & Missile Rocket Propulsion
Quantity of RDT&E Articles
FY 2004
Actual
11.649
0
FY 2005
Estimate
5.986
0
FY 2006
Estimate
6.627
0
FY 2007
Estimate
4.784
0
FY 2008
Estimate
4.787
0
PROJECT NUMBER AND TITLE
FY 2009
Estimate
5.191
0
FY 2010
Estimate
5.301
0
FY 2011
Estimate
5.400
0
Cost to
Complete
Continuing
Total
TBD
(U) A. Mission Description and Budget Item Justification
This project develops and demonstrates technologies for the sustainment of strategic systems (including solid boost/missile propulsion, Post Boost Control, and aging
and surveillance efforts) and tactical rockets. Characteristics such as environmental acceptability, affordability, reliability, reduced weight, and reduced operation and
launch costs are emphasized. Increased life and performance of propulsion systems are key goals. Technology areas investigated include ground demonstrations of
compact, lightweight, advanced propulsion systems, higher efficiency energy conversion systems (derived from an improved understanding of combustion
fundamentals), and high-energy propellants. Technological advances developed in this program are being accomplished in two phases and that could improve the
performance of expendable systems' payload capabilities by approximately 15 percent (Phase I)/20 percent (Phase II) and reduce hardware and operation costs by
approximately 25 percent (Phase I)/30 percent (Phase II). Aging and Surveillance efforts that could improve lifetime prediction capabilities by 10 years and reduce
non-destructive test costs by 50 percent. The projects in this program are part of the Technologies for the Sustainment of Strategic Systems program and support the
Integrated High Payoff Rocket Propulsion Technology program.
(U) B. Accomplishments/Planned Program ($ in Millions)
(U) MAJOR THRUST: Develop and demonstrate missile propulsion and Post Boost Control Systems
(PBCS) technologies for ballistic missiles.
(U) In FY 2004: Demonstrated component technologies with readily available materials to reduce hardware
costs with increased performance for the PBCS. Furthered hardware development integrating case,
nozzle, insulation, and propellant for the Missile Propulsion Demonstration Phase I.
(U) In FY 2005: Complete Phase I full-scale risk reduction component developments for the advanced PBCS
demonstration. Complete demonstration of component technologies with readily available materials to
reduce hardware costs with increased performance for the PBCS. Enhance hardware development
integrating case, nozzle, insulation, and propellant for the Missile Propulsion Demonstration Phase I.
(U) In FY 2006: Continue hardware development integrating case, nozzle, insulation, and propellant for the
Missile Propulsion Demonstration Phase I.
(U) In FY 2007: Complete the Missile Propulsion Demonstration Phase I.
(U)
(U) MAJOR THRUST: Develop and demonstrate missile propulsion, PBCS, aging, and surveillance
technologies for strategic systems. Efforts support the Technology for Sustainment of Strategic Systems
Phase II. Note: The FY 2005 start of subcomponent development for the propulsion demonstration
efforts was delayed to FY 2007 to allow for modeling and simulation tools to mature. After FY 2006,
the aging and surveillance efforts in this activity will become a separate activity in this project.
Project 4922
R-1 Shopping List - Item No. 20-15 of 20-22
401
UNCLASSIFIED
FY 2004
7.024
FY 2005
2.417
FY 2006
2.284
FY 2007
0.970
4.625
3.569
3.943
3.208
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4922 Space & Missile Rocket
Power Technology
Propulsion
(U) In FY 2004: Completed initial development of advanced modeling and simulation tools (Phase II)
applying them to actual missile components for verification, design, and modification. Began
development of advanced aging and surveillance models and tools to further improve capability to
analyze and predict motor life and system health.
(U) In FY 2005: Continue modeling and simulation tools (Phase II) development for analyzing and
developing missile components. Complete this development effort of aging and surveillance tools for
predicting the health of solid rocket motors. Develop methods to apply these tools on a motor-by-motor
basis vice a fleet wide basis.
(U) In FY 2006: Continue modeling and simulation tools (Phase II) development for analyzing and
developing missile components.
(U) In FY 2007: Begin development of subcomponents to test the accuracy of the previously developed
modeling and simulation tools and update the models with the resulting data for use in an upcoming
Missile Propulsion demonstration.
(U)
(U) MAJOR THRUST: Develop and demonstrate aging and surveillance technologies for strategic systems
to improve lifetime prediction capabilities by 10 years and reduce non-destructive test costs by 50
percent. Efforts support the Technology for Sustainment of Strategic Systems Phase II. Note: Prior to
FY 2006, the aging and surveillance efforts were part of another effort in this Project.
(U) In FY 2004: Not Applicable.
(U) In FY 2005: Not Applicable.
(U) In FY 2006: Complete development of aging and surveillance tools for predicting the health of solid
rocket motors and methods to apply these tools on a motor-by-motor basis vice a fleet wide basis.
(U) In FY 2007: Initiate scale-up activities for an advanced service life prediction program integrating
existing and advanced sensors, models, and tools to be able to predict the service life of a solid rocket
motor on a motor-by-motor basis.
(U) Total Cost
(U) C. Other Program Funding Summary ($ in Millions)
FY 2004
FY 2005
Actual
Estimate
(U) Related Activities:
(U) PE 0602102F, Materials.
PE 0602203F, Aerospace
(U)
Propulsion.
Project 4922
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
R-1 Shopping List - Item No. 20-16 of 20-22
402
UNCLASSIFIED
PROJECT NUMBER AND TITLE
0.000
0.000
0.400
0.606
11.649
5.986
6.627
4.784
FY 2009
Estimate
FY 2010
Estimate
FY 2011
Estimate
Cost to
Total Cost
Complete
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
Exhibit R-2a, RDT&E Project Justification
DATE
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
PROJECT NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 4922 Space & Missile Rocket
Power Technology
Propulsion
(U) C. Other Program Funding Summary ($ in Millions)
PE 0602601F, Spacecraft
(U)
Technology.
PE 0603401F, Advanced
(U)
Spacecraft Technology.
PE 0603500F,
(U) Multi-Disciplinary Adv Dev
Space Tec.
PE 0603853F, Evolved
(U) Expendable Launch Vehicle
Program.
PE 0603114N, Power
(U) Projection Advanced
Technology.
This project has been
coordinated through the
(U) Reliance process to
harmonize efforts and
eliminate duplication.
(U)
D. Acquisition Strategy
Not Applicable.
Project 4922
R-1 Shopping List - Item No. 20-17 of 20-22
403
UNCLASSIFIED
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
PROJECT NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 5098 Advanced Aerospace
Power Technology
Propulsion
FY 2004
FY 2005
FY 2006
FY 2007
FY 2008
FY 2009
FY 2010
FY 2011
Cost to
Total
Actual
Estimate
Estimate
Estimate
Estimate
Estimate
Estimate
Estimate
Complete
5098 Advanced Aerospace Propulsion
14.433
26.069
23.212
33.780
22.494
23.471
23.964
24.411 Continuing
TBD
Quantity of RDT&E Articles
0
0
0
0
0
0
0
0
Note: In FY 2005-2007, funds were shifted to accelerate the Air Force scramjet flight demonstration efforts. In 2007, funding increases to support ground demonstrations and
fabricate test vehicles for out-year flight demonstrations.
Cost ($ in Millions)
(U) A. Mission Description and Budget Item Justification
This project develops and demonstrates via ground and flight tests the scramjet propulsion cycle to a technology readiness level appropriate for full integration with
other engine cycles (including turbine and rocket-based) to provide the Air Force with transformational military capabilities. The primary focus is on the
hydrocarbon-fueled, scramjet engine. Multi-cycle engines will provide the propulsion systems necessary to support aircraft and weapon platforms operating over the
range of Mach 0 to 8+. Efforts include scramjet flow-path optimization to enable operation over the widest possible range of Mach numbers, active combustion
control to assure continuous positive thrust (even during mode transition), robust flame-holding to maintain stability through flow distortions, and maximized
volume-to-surface area to minimize the thermal load imposed by the high-speed engine. Thermal management plays a vital role in scramjet and combined cycle
engines, including considerations for protecting low speed propulsion systems (e.g.; turbine engines) during hypersonic flight.
(U) B. Accomplishments/Planned Program ($ in Millions)
(U) MAJOR THRUST: Develop and demonstrate technologies for a hydrocarbon-fueled scramjet with
robust operation over a range of Mach 4 to 8.
(U) In FY 2004: Designed and fabricated a fixed geometry flow-path for a hydrocarbon-fueled scramjet with
robust operations over a range of Mach 4.5 to 7+ to include optimization of the flow-path cross-section
and the flame-holding/fuel-mixing geometry. Developed a robust engine start system to achieve full
engine light after boost to Mach 4.5. Initiated design of an active engine sense-control system to manage
start transient and engine mode changes during acceleration. Initiated vehicle design capable of
rocket-boost to Mach 4, full integration with scramjet engine and hydrocarbon fuel system, and
acceleration from Mach 4.5 to 7+. Initiated selection of rocket boosters.
(U) In FY 2005: Ground test the flight weight hydrocarbon-fueled, fixed geometry flow path. Demonstrate
engine start and control systems. Continue detailed design of the scramjet engine demonstrator air
vehicle. Conduct wind tunnel tests of the air vehicle models to determine aerodynamic forces and
moments and vehicle stability and control. Conduct various design trade studies to ready the overall
demonstrator design (includes air vehicle structures, avionics, instrumentations, scramjet propulsion
systems, and boosters) for a critical design review.
(U) In FY 2006: Continue detailed design of the scramjet engine demonstrator air vehicle. Complete vehicle
subsystem trade studies and designs for structures, avionics, instrumentation, booster and other necessary
technologies. Conduct multiple risk reduction tests and analyses to reduce both aerodynamic and
Project 5098
R-1 Shopping List - Item No. 20-18 of 20-22
404
UNCLASSIFIED
FY 2004
14.433
FY 2005
26.069
FY 2006
23.212
FY 2007
33.780
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 5098 Advanced Aerospace
Power Technology
Propulsion
propulsion uncertainties prior to Critical Design Review. Conduct extensive transonic, supersonic, and
hypersonic wind tunnel tests and simultaneously conduct computational fluid dynamics analyses of tested
configurations. Conduct aero-thermodynamic tests to ensure vehicle thermal protection system design
meets requirements. Conduct additional propulsion related risk reduction tests to mature propulsion
system subcomponents (hot gas valves, digital engine controller, fuel pump) and broaden the engine
ground test matrix to better align with expected flight profiles.
(U) In FY 2007: Complete engine and vehicle designs and conduct vehicle critical design review. Fabricate
and test flight clearance engine and initiate fabrication of flight engines. Establish flight test profiles and
margins. Initiate fabrication of air vehicle flight hardware and begin flight test preparations at supporting
test centers.
(U) Total Cost
(U) C. Other Program Funding Summary ($ in Millions)
FY 2004
FY 2005
Actual
Estimate
(U) Related Activities:
(U) PE 0602102F, Materials
PE060203F, Aerospace
(U)
Propulsion
This project will be
coordinated through the
(U) Reliance process to
harmonize efforts and
eliminate duplication.
(U)
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
PROJECT NUMBER AND TITLE
14.433
FY 2009
Estimate
FY 2010
Estimate
26.069
FY 2011
Estimate
23.212
33.780
Cost to
Total Cost
Complete
D. Acquisition Strategy
Not Applicable
Project 5098
R-1 Shopping List - Item No. 20-19 of 20-22
405
UNCLASSIFIED
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 681B Advanced Turbine Engine Gas
Power Technology
Generator
Cost ($ in Millions)
681B
Advanced Turbine Engine Gas
Generator
Quantity of RDT&E Articles
FY 2004
Actual
FY 2005
Estimate
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
PROJECT NUMBER AND TITLE
FY 2009
Estimate
FY 2010
Estimate
FY 2011
Estimate
Cost to
Complete
27.192
25.954
24.775
25.532
25.546
27.706
28.287
28.812
0
0
0
0
0
0
0
0
Total
Continuing
TBD
(U) A. Mission Description and Budget Item Justification
This project develops and demonstrates technology to increase turbine engine operational reliability, durability, mission flexibility, and performance while reducing
weight, fuel consumption, and cost of ownership. The objective is to provide the continued evolution of technologies into an advanced gas generator in which the
performance, cost, durability, reparability, and maintainability can be assessed in a real engine environment. The gas generator, or core, is the basic building block of
the engine and it consists of a compressor, a combustor, a high-pressure turbine, mechanical systems, and core subsystems. Experimental core engine testing enhances
early, low-risk transition of key engine technologies into engineering development, where they can be applied to derivative and/or new systems. These technologies
are applicable to a wide range of military and commercial systems including aircraft, missiles, land combat vehicles, ships, and responsive space launch. Component
technologies are demonstrated in a core (sub-engine) test. This project also assesses the impact of low spool components (such as inlet systems, fans, low pressure
turbines, and exhaust systems) and system level technologies (such as integrated power generators and thermal management systems) on core engine performance and
durability. The core performances of this project are proven in demonstrator engines in Project 4921 of this PE. Efforts are part of the IHPTET and the VAATE
programs.
(U) B. Accomplishments/Planned Program ($ in Millions)
(U) MAJOR THRUST: Design, fabricate, and performance test demonstration core engines, using advanced
materials to provide greater durability, improved performance, and reduced fuel consumption for
turbofan/turbojet engines for fighters, attack aircraft, bombers, sustained supersonic and hypersonic
cruise vehicles, and large transports. Each of these technology innovations can be applied to a significant
part of the Air Force's engine inventory and offer potentially significant performance enhancements to
future aircraft engines, thus enabling new capabilities for faster, survivable, durable, more responsive
systems with longer range and greater payloads. Note: In FY 2005, funding was redirected to refocused
Air Force priorities that address propulsion needs for new capabilities such as advanced fighter-attack,
precision long-range strike, persistent high-altitude endurance, and agile combat support.
(U) In FY 2004: Completed advancement of hardware fabrication of a core engine test article with advanced
compressor aerodynamics, a trapped vortex combustor with ceramic matrix composite combustor liners,
magnetic bearings, and advanced turbine blisk and vane materials. Improved the design of hardware for
core engine test of a high-pressure ratio six-stage compressor with an integrated lightweight combustor
with integrated vane pack, a cooled cooling air system, and micro-circuit cooled high pressure turbine
blades with advanced thermal barrier coating.
(U) In FY 2005: Complete design and fabrication of hardware for testing a cooled-cooling air system,
Project 681B
R-1 Shopping List - Item No. 20-20 of 20-22
406
UNCLASSIFIED
FY 2004
22.532
FY 2005
21.635
FY 2006
21.334
FY 2007
21.980
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 681B Advanced Turbine Engine Gas
Power Technology
Generator
micro-circuit cooled high pressure turbine blades, and blade outer air seals with advanced thermal barrier
coating. Perform risk reduction tests of a magnetic bearing system for an advanced core engine. Initiate
conceptual studies and preliminary designs of advanced core engine technologies, including systems
level technologies residing within the core.
(U) In FY 2006: Complete preliminary design and begin detailed design of advanced core engine
technologies, including advanced turbine blade materials incorporating next generation cooling schemes,
novel coatings to reduce combustor and turbine heat loads, ceramic turbine components, and systems for
active control, thermal management, and power extraction. Begin preliminary design and risk reduction
planning for a tip turbine concept, including a novel compression system, innovative annular combustor,
and advanced rotating seals. Begin design of unique compression system components.
(U) In FY 2007: Complete detailed design and begin fabrication of advanced core engine technologies,
including advanced turbine blade materials incorporating next generation cooling schemes, novel
coatings to reduce combustor and turbine heat loads, ceramic turbine components, and systems for active
control, thermal management, and power extraction. Complete preliminary design and risk reduction
planning for a tip turbine concept, including a novel compression system, innovative annular combustor,
and advanced rotating seals. Continue design and begin fabrication of unique compression system
components.
(U)
(U) MAJOR THRUST: Design, fabricate, and durability test demonstration core engines to provide
increased durability and affordability for turbofan/turbojet engines for fighters, attack aircraft, bombers,
sustained supersonic and hypersonic cruise vehicles, and large transports. Note: Beginning in FY 2006,
this effort will be transferred to the remaining thrusts in this project since durability efforts are integral to
Air Force turbine efforts.
(U) In FY 2004: Enhanced the design and furthered the fabrication of long lead hardware for turbine engine
advanced core evaluations in the national durability program.
(U) In FY 2005: Complete the design and fabrication of long lead hardware for evaluation in the national
durability program.
(U) In FY 2006: Not Applicable.
(U) In FY 2007: Not Applicable.
(U)
(U) MAJOR THRUST: Design, fabricate, and evaluate technology demonstration core engines to provide
improved performance, greater durability, and lower fuel consumption for turboshaft/turboprop and small
turbofan engines for trainers, rotorcraft and runway independent air vehicles, special operations aircraft,
theater transports, and large unmanned air vehicles.
Project 681B
R-1 Shopping List - Item No. 20-21 of 20-22
407
UNCLASSIFIED
PROJECT NUMBER AND TITLE
1.506
1.500
0.000
0.000
3.154
2.819
3.441
3.552
Exhibit R-2a (PE 0603216F)
UNCLASSIFIED
DATE
Exhibit R-2a, RDT&E Project Justification
February 2005
BUDGET ACTIVITY
PE NUMBER AND TITLE
03 Advanced Technology Development (ATD)
0603216F Aerospace Propulsion and 681B Advanced Turbine Engine Gas
Power Technology
Generator
(U) In FY 2004: Conducted core engine tests of a forward swept splittered compressor rotor, a high
temperature rise combustor, a counter-rotating vaneless turbine, ceramic matrix composite turbine blades
and vanes, and magnetic bearings.
(U) In FY 2005: Complete core engine tests of a forward swept splittered compressor rotor, a high
temperature rise combustor, a counter-rotating vaneless turbine, ceramic matrix composite turbine blades
and vanes, and magnetic bearings. Initiate design of small versatile affordable core engine technologies.
(U) In FY 2006: Further the design and begin selective risk reduction tests of UAV small versatile affordable
advanced core engine technologies including a high heat release combustor, durable high performance
turbine, nanolaminate coatings, and systems for thermal management and advanced power extraction.
Begin planning for multi-Service demonstration of heavy fuel engine technologies for future rotorcraft.
(U) In FY 2007: Complete design, initiate hardware fabrication, and continue selective risk reduction tests of
UAV small versatile affordable advanced core engine technologies including a high heat release
combustor, durable high performance turbine, nanolaminate coatings, and systems for thermal
management and advanced power extraction. Continue planning for multi-Service demonstration of
heavy fuel engine technologies for future rotorcraft.
(U) Total Cost
(U) C. Other Program Funding Summary ($ in Millions)
FY 2004
FY 2005
Actual
Estimate
(U) Related Activities:
PE 0602201F, Aerospace
(U)
Flight Dynamics.
PE 0602203F, Aerospace
(U)
Propulsion.
PE 0603003A, Aviation
(U)
Advanced Technology.
This project has been
coordinated through the
(U) Reliance process to
harmonize efforts and
eliminate duplication.
(U)
FY 2006
Estimate
FY 2007
Estimate
FY 2008
Estimate
PROJECT NUMBER AND TITLE
27.192
FY 2009
Estimate
FY 2010
Estimate
25.954
FY 2011
Estimate
24.775
25.532
Cost to
Total Cost
Complete
D. Acquisition Strategy
Not Applicable.
Project 681B
R-1 Shopping List - Item No. 20-22 of 20-22
408
UNCLASSIFIED
Exhibit R-2a (PE 0603216F)